Aircraft interior flooring systems

ABSTRACT

An aircraft flooring system for an aircraft fuselage adapted to secure a payload component may include first and second seat tracks extending longitudinally with respect to the aircraft fuselage, the first and second seat tracks being spaced from one another; and an intercostal assembly extending between the first and second seat tracks. The intercostal assembly can include a first intercostal having a center member having a first end and a second end and a top flange including a mounting region between the first and second ends; and at least first and second tab members. The first tab member can be coupled to the top flange toward the first end of the center member and the second tab member can be coupled to the top flange toward the second end of the center member. The first and second tab members can extend beyond the first and second ends of the center member, respectively, and be configured to be coupled to the first and second seat tracks.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application is a divisional of U.S. patent application Ser. No.14/747,987 filed Jun. 23, 2015, now allowed, which claims the benefit ofU.S. Provisional Patent Application No. 62/016,002, filed Jun. 23, 2014,all of which applications are hereby incorporated by reference in theirentireties.

BACKGROUND Technical Field

The present disclosure generally relates to flooring systems, and moreparticularly to aircraft interior flooring systems.

Description of the Related Art

An aircraft floor structure is generally constructed in a gridformation. In the longitudinal direction (i.e., forward-aft direction ofan aircraft fuselage), the floor structure may include a plurality ofseat tracks spaced apart in the lateral direction (i.e., the left-rightdirection of the aircraft fuselage with respect to its longitudinal orroll axis). The seat tracks are typically mounted on floor beams, whichgenerally extend in the lateral direction from one side of the aircraftfuselage body to the other. The floor beams are typically spaced apartin the longitudinal direction (i.e., forward-aft direction of theaircraft fuselage). A plurality of floor panels are coupled to the topof the floor structure, the floor panels generally being disposedbetween adjacent seat tracks.

Aircraft floor structure is generally constructed to withstand variousoperating conditions an aircraft experiences during its life cycle, andprovide strength, stability, attachment locations, etc., for payloadcomponents to be secured to the floor structure. By way of example, thepayload components that are secured to the floor structure includemonuments, seat assemblies, lavatories, galleys, etc. Conventional floorstructures of commercial aircraft, for example, are constructed to havefixed locations in relation to aircraft coordinates (i.e., X, Y, Z),where such payload components are to be mounted. To provide structuralsupport at such locations, an intercostal is typically secured betweenadjacent seat tracks. The intercostals are positioned to mate with anupper surface of respective seat track flanges. The intercostals includeinterface members to mate with the payload component attachment fittingwhich are fixed in position and are typically formed from the samematerial as the corresponding intercostal.

As a result of positional rigidity of such interface members,substantial modifications to floor structures, including the floorpanels are required to secure the payload components.

By way of example, the fixed location of an interface member, positionedsubstantially in the center of the intercostal, requires the floorpanels be split or otherwise significantly altered to avoidinterference, and then attached to the intercostal. Such modificationslead to increased labor and material costs, weight, inefficiencies,among other things.

Further, payload components are often positioned in customized andnon-standard locations, relocated, added, re-aligned, etc. By way ofexample, while for commercial aircraft, payload components may be lessfrequently re-configured or positioned in non-standard configurations,in aircraft used for transporting VIPs, heads of states, etc., the floorstructure requires substantial customization and reconfiguration,including installing multiple additional and/or different payloadcomponents, removal, addition, and/or shifting of seat assemblies. Insuch applications, for example, conventional floor structures requiresubstantial modifications, thus significantly increasing costs, weight,and certification requirements, and re-certification of several aircraftcomponents, such as the payload components, seat tracks, floor beams,etc.

BRIEF SUMMARY

According to one embodiment, an aircraft flooring system for an aircraftfuselage adapted to secure a payload component may be summarized asincluding first and second seat tracks extending longitudinally withrespect to the aircraft fuselage, the first and second seat tracks beingspaced from one another; and an intercostal assembly extending betweenthe first and second seat tracks. The intercostal assembly can include afirst intercostal having a center member having a first end and a secondend, opposing the first end, and a top flange including a mountingregion between the first and second ends; and at least first and secondtab members. The first tab member can be coupled to the top flangetoward the first end of the center member and the second tab member canbe coupled to the top flange toward the second end of the center member.The first and second tab members can extend beyond the first and secondends of the center member, respectively, the first tab member configuredto be coupled to the first seat track and the second tab memberconfigured to be coupled to the second seat track.

According to another embodiment, an intercostal assembly adapted tosupport a payload component and configured to be coupled to a first seattrack and a second seat track of an aircraft flooring system can besummarized as including a center member having a first end and a secondend, opposing the first end, and a top flange including a mountingregion between the first and second ends; and at least first and secondtab members. The first tab member can be coupled to the top flangetoward the first end of the center member and the second tab member canbe coupled to the top flange toward the second end of the center member.The first and second tab members can extend beyond the first and secondends of the center member, respectively, the first tab member configuredto be coupled to the first seat track and the second tab memberconfigured to be coupled to the second seat track.

According to another embodiment, an intercostal assembly adapted tosupport a payload component and configured to be coupled to a first seattrack and a second seat track of an aircraft flooring system can besummarized as including a first intercostal having two tab memberstoward respective opposing ends of the first intercostal, the two tabmembers of the first intercostal configured to be coupled to the firstand second seat tracks respectively; and a second intercostal having twoopposing tab members toward respective opposing ends of the secondintercostal, the two tab members of the second intercostal configured tobe coupled to the first and second seat tracks respectively, the secondintercostal spaced from the first intercostal when installed in theaircraft flooring system. The intercostal assembly may further include athird intercostal extending between the first and second intercostalsand having two opposing tab members toward respective opposing ends ofthe third intercostal, the two tab members of the third intercostalconfigured to be coupled to the first and second intercostalsrespectively; and a first payload coupling adaptor positioned toward anupper region of the first intercostal between the first and second tabmembers.

BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWINGS

FIG. 1 is a partial perspective view of an aircraft flooring systemaccording to one embodiment, with certain components removed forclarity.

FIG. 2 is an enlarged partial perspective view of a portion of theaircraft flooring system of FIG. 1.

FIG. 3A is an isometric view of an intercostal illustrated in FIG. 2,according to one embodiment.

FIG. 3B is a top elevational view of the intercostal of FIG. 3A.

FIG. 3C is a front elevational view of the intercostal of FIG. 3A.

FIG. 3D is a side elevational view of the intercostal of FIG. 3A.

FIG. 3E is a side elevational view of the intercostal of FIG. 3A with areinforcement member according to one aspect.

FIG. 4 is an enlarged partial perspective view of a portion of theaircraft flooring system of FIG. 1, according to one embodiment.

FIG. 5 is an enlarged partial top elevational view of a portion of theaircraft flooring system of FIG. 1, according to one embodiment.

FIG. 6 is an enlarged partial top elevational view of a portion of theaircraft flooring system of FIG. 1, according to one embodiment.

FIG. 7A is an enlarged partial top elevational view of a portion of theaircraft flooring system of FIG. 1, according to one embodiment.

FIG. 7B is a cross-sectional view of the aircraft flooring systemillustrated in FIG. 1, taken along lines 7B-7B.

FIG. 8 is an enlarged partial perspective view of a portion of theaircraft flooring system of FIG. 1, according to one embodiment.

FIG. 9 is an enlarged partial perspective view of a portion of theaircraft flooring system of FIG. 1, according to one embodiment.

FIG. 10 is an enlarged partial perspective view of a portion of theaircraft flooring system of FIG. 1, according to one embodiment.

FIG. 11A is an enlarged partial perspective view of a portion of theaircraft flooring system of FIG. 1, according to one embodiment.

FIG. 11B is a cross-sectional view of the aircraft flooring systemillustrated in FIG. 11A, taken along lines 11B-11B.

FIG. 11C is a cross-sectional view of the aircraft flooring systemillustrated in FIG. 11A, taken along lines 11C-11C.

DETAILED DESCRIPTION

It will be appreciated that, although specific embodiments of thesubject matter of this application have been described herein forpurposes of illustration, various modifications may be made withoutdeparting from the spirit and scope of the disclosed subject matter.Accordingly, the subject matter of this application is not limited tothe specific embodiments described in this disclosure.

In the following description, certain specific details are set forth inorder to provide a thorough understanding of various aspects of thedisclosed subject matter. However, the disclosed subject matter may bepracticed without these specific details. In some instances, well-knownstructures and methods of attaching structures have not been describedin detail to avoid obscuring the descriptions of other aspects of thepresent disclosure.

Unless the context requires otherwise, throughout the specification andclaims that follow, the word “comprise” and variations thereof, such as“comprises” and “comprising” are to be construed in an open, inclusivesense, that is, as “including, but not limited to.”

Reference throughout the specification to “one embodiment” or “anembodiment” means a particular feature, structure, or characteristicdescribed in connection with the embodiment is included in at least oneembodiment. Thus, the appearance of the phrases “in one embodiment” or“in an embodiment” in various places throughout the specification arenot necessarily all referring to the same aspect. Furthermore,particular features, structures, or characteristics may be combined inany suitable manner in one or more aspects of the present disclosure.

FIGS. 1 and 2 generally illustrate an aircraft flooring system 10according to an example embodiment including a payload component 12mounted thereon, with certain components having been removed forclarity. The aircraft flooring system 10 includes a plurality of spacedapart floor beams 14 extending laterally with respect to an aircraftfuselage longitudinal or roll axis, e.g., left-right direction, and aplurality of seat tracks 16 extending longitudinally with respect to theaircraft fuselage, e.g., forward-aft direction or parallel to thefuselage longitudinal or roll axis, to define a flooring grid 18. Aplurality of floor panels 20 are secured to the seat tracks 16. Thefloor panels 20 may extend in the lateral direction between a pair ofadjacent or intermediate seat tracks 16 or may extend laterally betweenmultiple seat tracks 16.

In general, the flooring grid 18 is constructed to provide structuralstrength and stability to the fuselage and payload components (e.g., 12)that may be mounted thereon. In one embodiment, intercostals (e.g., 22,24, 25, 26, 28, 30, 31, 32, 34, 38, 40, etc.) are coupled to the seattracks 16 to provide support at locations where the payload components12 are to be mounted. By way of example, FIG. 2 illustrates intercostals22, according to one embodiment, coupled to a pair of adjacent seattracks 16 and the floor panel 20.

Referring now to FIG. 2 and FIGS. 3A-3E, the intercostal 22 includes acenter member 42 and a pair of coupling members or tab members 44. Forclarity and without intention to limit the coupling or tab members, thecoupling members will be referred to herein as tab members 44. In oneembodiment, center member 42 includes a top flange 46 and a pair ofstiffeners 48. In one aspect, the top flange 46 is substantiallyrectangular shaped and includes a pair of substantially parallelopposing side edges 50, a first end 52 and a second end 54 extendingbetween the side edges 50 to define an external boundary. In one aspect,the top flange 46 includes a top surface 56 and a bottom surface 58.

In one embodiment, as noted above, the center member 42 includes a pairof stiffeners 48. The stiffeners 48 in one aspect can be substantiallyL-shaped and include an upstanding flange 60 and a base flange 62. Theupstanding flange 60 in one embodiment can extend vertically from thebottom surface 58 along a vertical axis 64 of the intercostal 22.

In one embodiment, the base flange 62 extends, for example at asubstantially perpendicular angle, from a lower edge of the upstandingflange 60 along a first axis 66 of the intercostal 22. In one aspect,the upstanding flange 60 of the stiffener 48 can be selectively sizedand shaped to extend vertically a certain distance and have certaindimensions (e.g., thickness, width, etc.).

In one embodiment, the base flange 62 of the stiffener 48 is selectivelysized and shaped to extend longitudinally (i.e., with respect to theIntercostal 22 parallel to a second axis 84) a certain distance and havecertain dimensions (e.g., thickness, width, etc.). In this manner, thestiffener 48 is selectively and optimally sized and shaped to providestructural rigidity to the intercostal 22 while avoiding adverseinterference with adjacent structures, such as floor beams 14, floorpanels 20, wiring, plumbing, etc. While embodiments of the intercostalillustrated in FIGS. 1 through 10 include a pair of L-shaped stiffeners48, in other embodiments, stiffeners may have different shapes (i.e.,I-shaped, hat-shaped, Z-shaped, etc.).

In one embodiment, the stiffeners 48 are spaced apart with respect tothe vertical axis 64 and are a mirror image of one another with respectto the vertical axis 64 to define a reinforcement member cavity 68. Inone embodiment, the reinforcement member cavity 68 is configured toreceive therein a reinforcement member 70. By way of example, accordingto one embodiment, FIG. 3E partially illustrates a reinforcement member70 which has a substantially I-shaped cross-section. In one embodiment,a top flange of the reinforcement member 70 is sized and shaped to bereceived in the reinforcement member cavity 68 and mate with the bottomsurface 58 of the top flange 46. In one aspect, the stiffeners 48 areselectively and optimally spaced apart with respect to the vertical axis64 to provide structural rigidity and avoid interference, and form thereinforcement member cavity 68 to optionally include additionalreinforcement members 70.

With continued reference to FIGS. 2 and 3A-3E, each of the pair of tabmembers 44 extend laterally in an opposite direction with respect to thefirst axis 66 of the intercostal 22. According to one embodiment, in thevertical direction, the tab members 44 extend upwardly with respect tothe top surface 56 of the top flange 46. In one aspect, the tab members44 are substantially rectangular shaped and include respective firstends 71 located proximal to the corresponding first and second edges 52,54, at least a portion of the center member 42 therebetween, defining amounting region 72.

The mounting region 72 is in one embodiment arranged to selectivelyposition the payload component 12 to be coupled to the intercostal 22.In one embodiment the intercostal may include or be coupled to aninterface fitting 74.

By way of example, FIG. 4 illustrates a payload component fitting 73according to one aspect, configured to couple the payload component 12to the aircraft flooring system 10 (FIG. 1) through the interfacefitting 74 (FIG. 3A). The interface fitting 74 can advantageously beselectively located within the mounting region 72 (FIG. 3A).

In one embodiment, as illustrated in FIGS. 3A and 3B, the mountingregion 72 may include coupling features, such as, for example, aplurality of apertures 78 extending through the top flange 46 of thecenter member 42. The apertures 78 can be arranged to be locatedanywhere within the mounting region 72, such that the interface fitting74 can be selectively located or relocated within the mounting region72. By way of example, the interface fitting 74 can include interfacefitting coupling features, such as, for example, interface fittingapertures 43. The interface fitting apertures 43 are configured to allowthe interface fitting 74 to be removably coupled to the intercostal 22.Thus, the payload component 12 can be selectively coupled to theaircraft flooring system 10 (FIG. 1) via fasteners extending through thepayload component fitting 73 and the interface fitting 74.

Moreover, the mounting region 72 in one embodiment allows variousinterface fittings with a wide variety of orientations, shapes, andsizes to be mounted within the mounting region 72. By way of example,FIG. 5 illustrates the intercostal 22 removably coupled to an interfacefitting 80, according to one embodiment.

According to one aspect, the interface fitting 80 can be oriented withtwo opposing edges thereof extending substantially parallel to the sideedges 50 of the center member 42 (e.g., rotated 90 degrees with respectto the first axis 66 of the intercostal 22).

According to one embodiment, FIG. 6 illustrates an enlarged partial viewof an arrangement of a pair of intercostals 22 located adjacent to oneanother and coupled to two seat tracks 16. In one aspect, thisarrangement includes an interface fitting 82 according to oneembodiment. In one aspect, the interface fitting 82 extends from oneintercostal 22 to the other adjacent intercostal 22. The interfacefitting 82 can be oriented and arranged to be mounted to adjacentmounting regions 72 of the respective intercostals 22.

In various embodiments, the mounting regions 72 of the intercostals 22can be configured to be removably coupled to a wide variety of interfacefittings, which can be shaped, arranged and/or oriented in any mannerdesired, which allows the payload component 12 and its payload componentfitting 73 to be selectively arranged, moved, located, or relocated toany desired position.

In one embodiment, the tab members 44 extend outwardly from therespective first ends 71 along the second axis 84 of the intercostal 22toward a respective second end 86. In one aspect, the tab members 44protrude from the respective first and second edge 52, 54 of the topflange 46 of the center member 42 to define a mating region 88 (FIG.3C). In one embodiment, the mating region 88 is located in a lowersurface 90 (FIG. 3C) of the tab members 44 and is configured to becoupled to a top surface of the seat track 16 (e.g., top surface of atop seat track flange).

In one aspect, the tab members 44 also include coupling features, suchas, for example, a plurality of seat track apertures 41. The seat trackapertures 41 are located in the mating region 88 and extend through thetab members 44. In one embodiment, the seat track apertures 41 can havea substantially hexagonal shape and be configured to receivetherethrough corresponding fasteners to couple the tab members 44 to theseat tracks 16. It is appreciated that in some embodiments, the seattrack apertures 41 may comprise different shapes, such as circular, forexample.

In one embodiment, the intercostal 22 can be monolithically formed,comprising an integral or unitary body. For example, the intercostal 22can be formed using a machining process, extrusion process, moldingprocess (e.g., injection molding processes), vacuum forming (e.g.,vacuum bag molding), combinations thereof, or the like. However, it isappreciated that embodiments of the intercostal 22 comprising separatecomponents coupled together are also within the spirit and scope of thedisclosed subject matter.

With reference to FIGS. 1 through 3E, in one embodiment, the floorpanels 20 extend laterally to at least a pair of adjacent seat tracks 16and are coupled thereto. In one aspect, the lower surface of the floorpanel 20 is coupled to the top surface of the seat track 16. In oneaspect, the floor panel 20 includes end regions 92 located at opposingends of the floor panels 20 and a center region 94 located between theend regions 92. In one embodiment, the end regions 92 include notches 96located proximal to the tab members 44.

The notches 96 in some embodiments can include respective outer profileslocated at a periphery of the notches 96. The outer profiles of thenotches 96 can in some aspects be sized and shaped to enclose, bepositioned adjacent to, and/or substantially circumscribe an outerprofile of the respective tab members 44. As best illustrated in FIG. 1,in some embodiments, the center regions 94 of the floor panels 20 caninclude a center notch 98 located proximal the mounting region 72. Thecenter notch 98 in one embodiment includes respective outer profileslocated at a periphery of the center notch 98. In some aspects, outerprofiles of the center notch 98 can be sized and shaped to enclose, bepositioned adjacent to, and/or substantially circumscribe an outerprofile of the interface fitting 74.

In some embodiments, as illustrated in FIG. 2, the center region 94 ofthe floor panel 20 can extend continuously between the end regions 92such that the lower surface of the floor panel in the center region 94substantially abuts or contacts, or is otherwise adjacent, the mountingregion 72 (FIGS. 3A and 3B) of the intercostal 22. In this manner,having a mounting region 72 capable of excluding an interface fitting(e.g., 76) provides significant manufacturing and assembly flexibility,thus resulting in cost savings, such as manufacturing and labor costs,for example. Further, unnecessarily reinforcing the floor panels withadditional structure, expending resources (e.g., engineering)re-designing and/or analyzing, or re-certifying the floor panels to meetcertain regulatory requirements can advantageously be avoided byselectively excluding, locating, or relocating interface fittings.

FIG. 7A is an enlarged partial plan view of a portion of the aircraftflooring system 10 (FIG. 1). FIG. 7B is a cross-sectional view takenalong Section 7B-7B in FIG. 7A. FIGS. 7A and 7B illustrate anintercostal 38 according to another embodiment. The intercostal 38provides a variation in which the intercostal 38 includes one tab member44 (FIG. 1) at one end and a slideable tab member 100 at the other end.The tab member 44 is configured to be coupleable to the seat track 16,for example, fixedly coupleable thereto. In one embodiment, the tabmember 44 and the slideable tab member 100 extend laterally in anopposite direction with respect to a longitudinal axis of theintercostal 38 in a manner similar to that described previously withrespect to the other embodiments.

In the vertical direction, the slideable tab member 100 extends upwardlywith respect to a top surface 104 of a top flange 102 of the centermember 106 of the intercostal 38. In one aspect, the slideable tabmember 100 includes an interface portion 108 and a slipped end portion110. The interface portion 108 can be substantially rectangular shapedand include a first end 112 located toward a central region of thecenter member 106 of the intercostal 38 and a second end 114 locatedproximal to a first edge 116 of the center member 106. In oneembodiment, the slipped end portion 110 extends away from the second end114 of the interface portion 108 and gradually tapers downwardly along avertical axis 118 of the intercostal 38.

According to one embodiment, the slipped end portion 110 protrudesoutwardly from the second end 114 of the interface portion 108 extendingto a slipped end 120 to define a mating region 122 of the slideable tabmember 100. In one aspect, the mating region 122 is located proximal alower surface of the slideable tab member 100 and a top surface of theseat track 16 when the intercostal 38 is coupled to the seat track 16.In one embodiment, the intercostal 38 optionally includes a pair ofmating plates 124 and a washer plate 126. The mating plates 124 may befabricated from a suitable material, including but not limited, tonylon, various polymers, or any other material having suitable reducedfriction or non-friction properties. The washer plate 126 may befabricated from a suitable material, including but not limited, tosteel, aluminum, titanium, various polymers, or any other suitablematerial. One of the mating plates 124 is positioned between the lowersurface of the slideable tab member 100 and the top surface of the seattrack 16 and the other mating plate 124 is positioned between the washerplate 126 and a top surface of the slideable tab member 100 to define amulti-layered connection of the intercostal 38 to the seat track 16 atone end of the intercostal 38.

In one embodiment, proximal the slipped end 120 of the slipped endportion 110, the slipped end portion 110 includes a pair of spaced apartslideable notches 128. The slideable notches 128 in some aspects can besubstantially horseshoe shaped and extend toward the slipped end 120 ofthe slipped end portion 110 to define respective free edges. Thehorseshoe shaped slideable notches 128 advantageously allow theintercostal 38 to be slideably coupled to the seat track 16. In thismanner, the intercostal 38 is moveable in the lateral direction whilebeing substantially restrained in the longitudinal direction.Consequently, the intercostal 38 can advantageously allow for relativelateral movement of adjacent seat tracks 16, which may be caused due toaircraft fuselage deflection. Further, the slideable tab member 100 canimprove assembly processes of the intercostal 38 by allowing theintercostal 38 to be moveable in the lateral direction to minimize orlimit effects of eccentricities that may result due to manufacturingtolerances and/or defects.

FIG. 8 is an enlarged partial view of a portion of the aircraft flooringsystem 10 (FIG. 1) illustrating an intercostal 31 according to oneembodiment. The intercostal 31 of the illustrated embodiment of FIG. 8provides a variation in which the intercostal 31 extends between a pairof end seat tracks 16A and an intermediate seat track 16B locatedbetween the pair of end seat tracks 16A. The intercostal 31 in oneaspect includes a first portion 132, a second portion 134, and anintermediate tab member 136 located in between the first and secondportions 132, 134. The first and second portions 132, 134 includerespective center members 138, 139. According to one aspect, the firstportion 132 includes a tab member 144 and the second portion 134includes a slideable tab member 150. The center members 138, 139, thetab member 144, and the slideable tab member 150 in some embodiments aregenerally similar to those respectively described previously accordingto other embodiments.

In one aspect, the first and second portions 132, 134 are spaced apartto define a receiving cavity 146. The receiving cavity 146 can be sizedand shaped to receive therein the intermediate seat track 16B. Accordingto one embodiment, the tab member 144, the slideable tab member 150, andthe intermediate tab member 136 extend upwardly in a vertical directionwith respect to top surfaces of center members 138, 139 of the first andsecond portions 132, 134 of the intercostal 31 such that respectivelower surfaces of the tab member 144 and the slideable tab member 150substantially abut or contact a top surface of the end seat tracks 16A,and a lower surface of the intermediate tab member 136 substantiallyabuts or contacts a top surface of the intermediate seat track 16B whenthe intercostal 31 is coupled to the end and intermediate seat tracks16A, 16B.

In this variation of the intercostal 31, the tab member 144 and theintermediate tab member 136 are fixedly coupled to one of the end seattracks 16A and the intermediate seat track 16B, respectively. Theslideable tab member 150 is slideably coupled to the other end seattrack 16A. In this manner, the intercostal 31 can advantageously bemoveable in the lateral direction and be restrained in the longitudinaldirection.

In other embodiments, the intermediate tab member can be configured tobe slideable depending on the level of movement anticipated or desired.

FIG. 9 is an enlarged partial view of a portion of the aircraft flooringsystem 10 (FIG. 1) illustrating an intercostal 25 according to oneembodiment. In the illustrated embodiment of FIG. 9, the intercostal 25provides a variation in which the intercostal 25 includes a centermember 241 having a first portion 245 and a second portion 247. Thefirst and second portions 245, 247 are spaced apart to define a cavity249. The cavity 249 of the intercostal 25 is configured to receivetherein a floor panel support beam 13. In one aspect, the intercostal 25includes an elongated tab member 243 at one end of the intercostal 25coupled to a seat track 16 and a tab member 244 at the other end of theintercostal 25. The elongated tab member 244 extends further inwardtoward a center of the intercostal 25 as compared to the tab member 244.In one embodiment, the tab member 244 extends between the first andsecond portions 245, 247 and can be configured such that a lower surfaceof the tab member 244 substantially abuts or contacts a top surface ofthe floor panel support beam 13 when the intercostal 25 is coupled tothe seat track 16 and the floor panel support beam 13.

FIG. 10 is an enlarged partial view of a portion of the aircraftflooring system 10 (FIG. 1) illustrating an intercostal 32 according toyet another embodiment. In the illustrated embodiment of FIG. 10, theintercostal 32 provides a variation in which the intercostal 32 includesa spanning tab member 344. The spanning tab member 344 extends betweenopposite ends of the intercostal 32. In this variation of theintercostal 32, an interface fitting (e.g., 76) can be excluded oravoided, as the payload component fitting (e.g., 73) can be directlymounted to the intercostal 32. Moreover, in a similar manner, in thevarious embodiments of the intercostals discussed previously, in someembodiments the payload component fittings can be directly mounted totab members, slideable tab members, intermediate tab members, etc., inlieu of mounting the payload component fittings to the intercostalsthrough the interface fitting.

FIG. 11A is an enlarged partial view of a portion of the aircraftflooring system 10 (FIG. 1) illustrating an arrangement of a pair ofintercostals 412A, 412B located adjacent to one another and coupled totwo seat tracks 16. FIGS. 11B and 11C are cross-sectional views takenalong lines 11B-11B and 11C-11C, respectively, of the partial view ofthe aircraft flooring system 10 shown in FIG. 11A. In one aspect, thisarrangement includes a first payload coupling adaptor 414 coupled to theintercostals 412A, 412B and a second payload coupling adaptor 416coupled to one of the seat tracks 16.

More particularly, this arrangement is adapted to advantageously allowpayload components of a wide variety of commercial aircraft to be used,re-used, and/or positioned in a customized manner. For instance, payloadcomponents, such as aircraft seats, for example, are often modified,upgraded, or re-designed to be used in connection with different modelsof commercial aircraft, which results in specific aircraft seatssuitable for specific models of commercial aircraft. In such instances,aircraft seats of previous designs or ones used with previous models ofcommercial aircraft, for example, often cannot be re-used with newermodels of commercial aircraft, or vice versa. This arrangement allowspayload components, such as aircraft seats, for example, from a widevariety of commercial aircraft models to be used, re-used, and/orpositioned in a customized manner, as discussed in more detail below.

In some embodiments, the first payload coupling adaptor 414 can includean intercostal, beam, fitting, and/or other suitable structure. In someembodiments, the first payload coupling adaptor 414 can include opposingtab members coupled to the first and second intercostals 412A, 412B,respectively. In one aspect, at least one of the opposing tab members ofthe payload coupling adaptor 414 can be slidably coupled to thecorresponding one of the first and second intercostals 412A, 412B. Byway of example, in some embodiments, at least one of the opposing tabmembers may include a slipped end portion coupleable to thecorresponding intercostals 412A, 412B, such that the first payloadcoupling adaptor 414 can be moveable in a longitudinal direction and berestrained in the lateral direction.

In one aspect, the intercostals 412A, 412B provide a variation in whichthe intercostals 412A, 412B include a spanning tab member 444 and aslideable tab member 450. The spanning tab member 444 extends from oneend of the intercostals 412A, 412B toward the other, opposite end of theintercostals 412A, 412B. The spanning member 444 smoothly transitionsinto the slideable tab member 450 through a neck down or taperingportion 439. In one aspect, the slideable tab member 450 and thespanning member 444 are generally similar to the embodiments describedpreviously, such as, for example, slideable tab members 100, 150 andspanning tab member 344. By way of example, in one aspect, the spanningtab member 444 is fixedly coupleable to the seat track 16. By way offurther example, in one aspect, the slideable tab member 450 can includea slipped end portion 420 coupleable to the seat track 16 such that theintercostals 412A, 412B are moveable in a lateral direction and can berestrained in the longitudinal direction.

In another aspect, the intercostals 412A, 412B provide a variation inwhich the intercostals 412A, 412B include a recess 413 located on oneside thereof. The intercostal 412A includes the recess 413 located on aside 418A facing and adjacent to a side 418B of the intercostal 412B.The recesses 413 are configured to receive therein at least a portion ofthe first payload coupling adaptor 414.

The first payload coupling adaptor 414, according to one embodiment,includes a top flange 446 and a pair of stiffeners 448. In one aspect,the top flange 446 is substantially rectangular shaped and includes apair of substantially parallel opposing side edges 451, a first end 452and a second end 454 extending between the side edges 451 to define anexternal boundary. In one aspect, the top flange 446 includes a topsurface 456 and a bottom surface 458.

The stiffeners 448 in one aspect can be substantially C-shaped andinclude a pair of base or lower flanges 462A, 462B and an upstandingflange 460 extending therebetween. The upstanding flange 460 in oneembodiment can extend vertically from the bottom surface 458 along avertical axis 464 of the first payload coupling adaptor 414.

In one embodiment, the base flange 462B extends, for example at asubstantially perpendicular angle, from a lower edge of the upstandingflange 460 along a first axis 466 of the first payload coupling adaptor414. The base flange 462A extends, for example at a substantiallyperpendicular angle, from a side edge of the top flange 446 along thefirst axis 466. In one aspect, the upstanding flange 460 of thestiffener 448 can be selectively sized and shaped to extend vertically acertain distance and have certain dimensions (e.g., thickness, width,etc.).

In one embodiment, the base flanges 462A, 462B and the upstanding flange460 of the stiffener 448 are selectively sized and shaped to extendlongitudinally (i.e., with respect to the first coupling adaptor 414parallel to a second axis 484) a certain distance and have certaindimensions (e.g., thickness, width, etc.). In one aspect, the stiffener448 extends between the adjacent intercostals 412A, 412B a certaindistance such that opposing ends of the stiffeners 448 are received inthe recesses 413. In one aspect, the ends of the stiffeners 448 may abutor make substantial contact with respective mating surfaces of theintercostals 412A, 412B. In another aspect, the base flange 462Bincludes mating regions located at opposing ends thereof and configuredto couple the base flange 462B to stiffeners of adjacent intercostals412A, 412B. While the embodiment of the first coupling adaptorillustrated in FIGS. 11A-11C includes a pair of C-shaped stiffeners 448,in other embodiments, stiffeners may have different shapes (i.e.,I-shaped, hat-shaped, Z-shaped, etc.). In some embodiments, the baseflange 462B can be slidably coupled to the stiffeners of adjacentintercostals 412A, 412B, at least toward one end of the base flange462B. By way of example, in some embodiments, the base flange 462B mayinclude a slipped end portion or other similar member that can beconfigured to allow movement in the longitudinal direction and berestrained in the lateral direction.

In one embodiment, the stiffeners 448 are spaced apart with respect tothe vertical axis 464 and are a mirror image of one another with respectto the vertical axis 464 to define a reinforcement member cavity 468. Inone embodiment, the reinforcement member cavity 468 can be configured toreceive therein a reinforcement member, such as, for example, thereinforcement member 70. In one aspect, the stiffeners 448 areselectively and optimally spaced apart with respect to the vertical axis464 to provide structural rigidity and avoid interference, and form thereinforcement member cavity 468 to optionally include additionalreinforcement members.

In one aspect, the top flange 446 includes coupling features, such as,for example, adaptor apertures 481 located proximate to the first andsecond ends 452, 454. The adaptor apertures 481 are configured to couplethe top flange 446 to adjacent intercostals 412A, 412B. Moreparticularly, portions of the bottom surface 458 located proximate tothe first and second ends 452, 454 abut or make substantial contact withmounting regions 472A, 472B of the respective intercostals 412A, 412B,when the first payload coupling adaptor 414 is coupled thereto. In oneaspect, the top flange 446 includes a receptacle section 490 extendinglongitudinally along the second axis 484. The receptacle section 490includes a plurality of spaced apart circular portions 491 with lipportions 492 disposed therebetween. In one aspect, the receptaclesection 490 is configured to be coupled to an aircraft seat and to theflooring system 10. By way of example, an aircraft seat may include aframe having opposing ends configured to coupleably receive seat trackfittings. In one aspect, the aircraft seat may include a first seattrack fitting at one end of the frame which can be moveable along thelength of the receptacle section 490 to position the aircraft seatduring installation, relocation, or the like. The aircraft seat at theother end of the frame may include a second seat track fittingconfigured to be coupled to the second payload coupling adaptor 416.

In one aspect, the second payload coupling adaptor 416 includes a mainbody 422 having a bottom surface 423 that abuts or makes substantialcontact with a mating surface of the seat track 16, when the secondpayload coupling adaptor 416 is coupled thereto. The main body 422 ofthe second payload coupling adaptor 416 includes a channel 425 extendinglongitudinally in a direction that is substantially parallel to thesecond axis 484. The channel 425 includes spaced apart circular portions493 with lip portions 494 disposed therebetween. The channel 425 isconfigured to receive therethrough an aircraft seat fitting, such as thesecond seat track fitting discussed above, which is configured to couplean aircraft seat to the aircraft flooring system 10. The second seattrack fitting, therefore, can be moveable along the length of thechannel section 425 to position the aircraft seat during installation,relocation, or the like. The main body 422 further includes a pluralityof adaptor apertures 495 spaced apart in the longitudinal direction. Theadaptor apertures 495 are configured to couple the second payloadcoupling adaptor 416 to the seat track 16.

In one aspect, the first and second payload coupling adaptors 414, 416are advantageously configured to couple aircraft seats of a wide varietyof configurations to the aircraft flooring system 10. The second payloadcoupling adaptor 416, for example, can be adapted to receive seat trackfittings of a wide variety of aircraft seats used for various commercialaircraft models. The first payload coupling adaptor 414 can be similarlyadapted to receive seat track fittings of a wide variety of aircraftseats used for various commercial aircraft models. In another aspect,the first payload coupling adaptor 414 can be moved, positioned, orrepositioned along the first axis 466 to match footprints of a widevariety of aircraft seats.

The various embodiments of the intercostals and payload coupling adaptordescribed herein can be integral or one-piece embodiments of theintercostals. The intercostals and the payload coupling adaptors can bemonolithically formed using a machining process, extrusion process,molding process (e.g., injection molding processes), vacuum forming(e.g., vacuum bag molding), combinations thereof, and the like. Theintercostals and the payload coupling adaptors may comprise aluminum,titanium, various metallic alloys, carbon fiber reinforced plastic, orother materials with suitable properties. Moreover, the variousembodiments described above can be combined to provide furtherembodiments.

These and other changes can be made to the embodiments in light of theabove-detailed description. In general, in the following claims, theterms used should not be construed to limit the claims to the specificembodiments disclosed in the specification and the claims, but should beconstrued to include all possible embodiments along with the full scopeof equivalents to which such claims are entitled. Accordingly, theclaims are not limited by the disclosure.

The invention claimed is:
 1. An aircraft flooring system for an aircraftfuselage adapted to secure a payload component, the aircraft flooringsystem comprising: first and second seat tracks extending longitudinallywith respect to the aircraft fuselage, the first and second seat tracksbeing spaced from one another; an intercostal assembly extending betweenthe first and second seat tracks, the intercostal assembly including anintercostal having: a center member having a first end and a second end,opposing the first end, and a top flange including a mounting regionbetween the first and second ends; and at least first and second tabmembers, the first tab member coupled to the top flange toward the firstend of the center member, the second tab member coupled to the topflange toward the second end of the center member, the first and secondtab members extending beyond the first and second ends of the centermember, respectively, the first tab member configured to be coupled tothe first seat track and the second tab member configured to be coupledto the second seat track, and wherein the first tab member issubstantially static when coupled to the first seat track, and thesecond tab member is movably coupled to the second seat track, thesecond tab member being slideably moveable along a first axis andsubstantially static along a second axis, when coupled to the secondseat track.
 2. The aircraft flooring system of claim 1, furthercomprising: at least one interface fitting positioned between the firstand second tab members and coupled to the mounting region wherein themounting region and the interface fitting each include coupling featuresfacilitating removal and relocation of the interface fitting from afirst location of the mounting region to a second location thereof. 3.The aircraft flooring system of claim 1 wherein the second tab memberincludes an interface portion that includes a first end located toward acentral region of the center member and a second end located proximal toan edge of the center member.
 4. The aircraft flooring system of claim 1wherein the second tab member includes a slipped end portion thatextends away from an edge of the center member.
 5. The aircraft flooringsystem of claim 4 wherein the slipped end portion includes a notch thatis sized and shaped to slideably couple to the second seat track.
 6. Theaircraft flooring system of claim 5 wherein the notch at one end has aclosed face and at another, opposing end has an open face.
 7. Theaircraft flooring system of claim 1, further comprising: a pair ofplates, a first one of the pair of plates coupled to a top surface ofthe second tab member, and a second one of the pair of plates coupled toa lower surface of the second tab member and a top surface of the secondseat track.
 8. The aircraft flooring system of claim 7, furthercomprising: a washer plate coupled to the first one of the pair ofplates.
 9. The aircraft flooring system of claim 1, further comprising:at least one flange extending away from the top flange on opposinglateral sides of the top flange and forming opposing first and secondstiffeners and forming a reinforcement cavity therebetween.
 10. Anintercostal assembly adapted to support a payload component, theintercostal assembly configured to be coupled to a first seat track anda second seat track of an aircraft flooring system, the intercostalassembly including an intercostal comprising: a center member having afirst end and a second end, opposing the first end, and a top flangeincluding a mounting region between the first and second ends; and atleast first and second tab members, the first tab member coupled to thetop flange toward the first end of the center member, the second tabmember coupled to the top flange toward the second end of the centermember, the first and second tab members extending beyond the first andsecond ends of the center member, respectively, the first tab memberconfigured to be coupled to the first seat track and the second tabmember configured to be coupled to the second seat track, wherein thefirst tab member of the intercostal is substantially static when coupledto the first seat track, and the second tab member of the intercostal ismovably coupled to the second seat track, the second tab member of theintercostal being slideably moveable along a first axis andsubstantially static along a second axis, when coupled to the secondseat track.
 11. The intercostal assembly of claim 10 wherein the secondtab member includes a slipped end portion that extends away from an edgeof the center member.
 12. The intercostal assembly of claim 11 whereinthe slipped end portion includes a notch that is sized and shaped toslideably couple to the second seat track.
 13. The intercostal assemblyof claim 12 wherein the notch at one end has a closed face and atanother, opposing end has an open face.
 14. The intercostal assembly ofclaim 10, further comprising: at least one flange extending away fromthe top flange on opposing lateral sides of the top flange and formingopposing first and second stiffeners and forming a reinforcement cavitytherebetween.
 15. The intercostal assembly of claim 10, furthercomprising: a pair of plates, a first one of the pair of plates coupledto a top surface of the second tab member, and a second one of the pairof plates coupled to a lower surface of the second tab member and a topsurface of the second seat track.
 16. The intercostal assembly of claim15, further comprising: a washer plate coupled to the first one of thepair of plates.